CN109578083A - A kind of turbomachine and aero-engine - Google Patents
A kind of turbomachine and aero-engine Download PDFInfo
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- CN109578083A CN109578083A CN201710893824.XA CN201710893824A CN109578083A CN 109578083 A CN109578083 A CN 109578083A CN 201710893824 A CN201710893824 A CN 201710893824A CN 109578083 A CN109578083 A CN 109578083A
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- Prior art keywords
- cavity
- turbomachine
- stator
- preventing leakage
- drum barrel
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Architecture (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to a kind of turbomachine and aero-engines, wherein turbomachine includes device for preventing leakage, multiple stator blades (1) and multiple rotor blades (2), stator blade (1) and rotor blade (2) arranged for interval, the first cavity is formed between the side and rotor blade adjacent thereto (2) of stator blade (1), the second cavity is formed between the other side of stator blade (1) and another rotor blade (2) adjacent thereto, pressure of the pressure of first cavity less than the second cavity, device for preventing leakage is used to reduce the pressure difference between the first cavity and the second cavity, to reduce the flow for the leakage flow for flowing to the first cavity from the second cavity.The present invention can reduce the pressure difference between the first cavity and the second cavity by setting device for preventing leakage, weakens the driving force that air-flow is flowed from the second cavity to the first cavity, reduces the flow of leakage stream, to improve the efficiency and stability margin of turbomachine.
Description
Technical field
The present invention relates to aero-engine technology field more particularly to a kind of turbomachine and aero-engines.
Background technique
Core component of the compressor as aero-engine, performance have very important influence to complete machine.In order to drop
The oil consumption rate of low modern aeroengine, and improve the reliability of engine, it is desirable that compressor have higher pressure ratio, efficiency and
Stability margin.Aero-engine in actual operation, because of the needs of structure design, generally uses in the stator inner ring of compressor
Labyrinth gas seals structure, (stator blade and rotor blade are staggered the cavity of stator inner ring two sides, and cavity here refers to
Turn to be formed by chamber between stator) between have pressure difference, therefore will lead to stator inner ring generate gas leakage stream, this is to pressure
The efficiency and stability margin of mechanism of qi have very detrimental effect.Studies at home and abroad show that the raising of Capability of Compressor is largely
It is upper to depend on obturaging the improvement of technology and the reduction of leakage flow, therefore how to improve labyrinth air seals, reduce stator cavity
Leakage rate, improve compressor efficiency, widen compressor stable operation range, be always compressor design in the key to be considered
One of problem.For turbine, needs to be improved or solve there is also identical problem.
In order to reduce the leakage flow of turbomachine cavity, reduction is generallyd use in currently available technology and turns to hold between stator grade
Cavity gap or the method for designing leakage stream suction unit.Method for reducing gap, since compressor is in different operating condition works
When making, the size in gap is variation, therefore not can guarantee all smaller in the stateful lower gap of institute, while gap is too small can also
Generate structure security risk；For the method for leakage stream suction, the mode of passive air-breathing guarantees suction effect without standard measure, and changes
It needs to increase a set of pumping equipment again additionally for active inspiration, to increase the overall weight of engine, being unable to satisfy loss of weight is needed
It asks.
Therefore, it needs to design a kind of novel device for reducing the leakage of turbomachine cavity.
It should be noted that the information for being disclosed in background of invention part is merely intended to increase to totality of the invention
The understanding of background, and be not construed as recognizing or imply in any form the information constitute by those skilled in the art public affairs
The prior art known.
Summary of the invention
The purpose of the present invention is to propose to a kind of turbomachine and aero-engines, to reduce stator blade two sides as much as possible
Cavity between pressure difference, weaken the driving of leakage stream, reduce leakage flow, improve the efficiency of turbomachine and stablize abundant
Degree.
To achieve the above object, the present invention provides a kind of turbomachine, including device for preventing leakage, multiple stator blades and
Multiple rotor blades, stator blade and rotor blade arranged for interval, the side of stator blade and rotor blade adjacent thereto it
Between form the first cavity, form the second cavity between the other side of stator blade and another rotor blade adjacent thereto, first
The pressure of cavity is less than the pressure of the second cavity, and device for preventing leakage is for reducing the pressure between the first cavity and the second cavity
Difference, to reduce the flow for the leakage flow for flowing to the first cavity from the second cavity.
Further, device for preventing leakage is arranged in the first cavity and/or the second cavity.
Further, turbomachine further includes multiple wheel discs, and rotor blade is mounted on wheel disc, between two neighboring wheel disc
It is connected by drum barrel, device for preventing leakage is arranged on drum barrel.
Further, device for preventing leakage and drum barrel are integrally formed；Alternatively, device for preventing leakage is welded on drum barrel.
Further, device for preventing leakage includes supercharging device, and supercharging device is arranged in the first cavity, so that the first cavity
Pressure rise；And/or device for preventing leakage includes dropping equipment, dropping equipment is arranged in the second cavity, so that the second cavity
Pressure reduction.
Further, supercharging device includes radial flow impeller machinery or mixed flow compressor tool；And/or dropping equipment packet
Include radial flow impeller machinery or mixed flow compressor tool.
Further, supercharging device includes centrifugal impeller；And/or dropping equipment includes centripetal turbine.
Further, turbomachine further includes multiple wheel discs, and rotor blade is mounted on wheel disc, between two neighboring wheel disc
It is connected by drum barrel, one end of the close drum barrel of stator blade is equipped with stator inner ring, the close device for preventing leakage of stator inner ring
Side is equipped with anti-abrasive coatings.
Further, there is gap between anti-abrasive coatings and device for preventing leakage.
Further, turbomachine further includes casing, and stator blade is mounted on casing, the close rotor blade of casing
Side is equipped with anti-abrasive coatings.
Further, turbomachine further includes multiple wheel discs, and rotor blade is mounted on wheel disc, between two neighboring wheel disc
It is connected by drum barrel, one end of the close drum barrel of stator blade is equipped with stator inner ring, and comb tooth is equipped between stator inner ring and drum barrel
Seal structure.
To achieve the above object, the present invention also provides a kind of aero-engines, including above-mentioned turbomachine.
Further, turbomachine includes turbine or compressor.
Based on the above-mentioned technical proposal, the present invention can reduce the first cavity and the second cavity by setting device for preventing leakage
Between pressure difference, weaken driving force from the second cavity to the first cavity that flow from of air-flow, reduce the flow of leakage stream, to mention
The efficiency and stability margin of high turbomachine.Moreover, with the increase of revolving speed, although the pressure between the first cavity and the second cavity
Difference can be increase accordingly, but the ability of device for preventing leakage reduction pressure difference can also increase with the increase of revolving speed, therefore can be adaptive
Ground meets the increased requirement of balance of pressure difference between the first cavity and the second cavity, and when revolving speed reduces, vice versa.
Detailed description of the invention
The drawings described herein are used to provide a further understanding of the present invention, constitutes part of this application, this hair
Bright illustrative embodiments and their description are used to explain the present invention, and are not constituted improper limitations of the present invention.In the accompanying drawings:
Fig. 1 is the leak pressure analysis chart for turning cavity between stator grade of compressor in the prior art.
Fig. 2 is the partial structural diagram of turbomachine one embodiment of the present invention.
Fig. 3 is the chamber pressure analysis chart of another embodiment of turbomachine of the present invention.
Fig. 4 is the chamber pressure analysis chart of another embodiment of turbomachine of the present invention.
In figure:
101, rotor blade；102, stator blade；103, stator inner ring；
1, stator blade；2, rotor blade；3, stator listrium；4, stator inner ring；5, wheel disc；6, drum barrel；7, centripetal turbine；
8, centrifugal impeller；9, first coating；10, second coating；11, the first gap；12, the second gap；13, third coating；14, it obturages
Comb tooth；15, honeycomb.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, is clearly and completely retouched to the technical solution in embodiment
It states.Obviously, described embodiment is only a part of the embodiments of the present invention, instead of all the embodiments.Based on this hair
Bright embodiment, every other implementation obtained by those of ordinary skill in the art without making creative efforts
Example, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that, term " center ", " transverse direction ", " longitudinal direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "upper", "lower", "vertical", "horizontal", "top", "bottom", "inner", "outside" is
It is based on the orientation or positional relationship shown in the drawings, is merely for convenience of description of the present invention and simplification of the description, rather than instruction or dark
Show that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as pair
The limitation of the scope of the present invention.
In the prior art, as shown in Figure 1, compressor includes rotor blade 101, stator blade 102 and and stator blade
The stator inner ring 103, P of 102 connectionsS1The static pressure of (import) on the left of the root of stator blade 102, due at this and in stator
103 left side cavity of ring is connected, therefore the static pressure in 103 left side of stator inner ring is also PS1；PS2On the right side of the root of stator blade 102
The static pressure of (outlet), due to being connected at this with 103 right side cavity of stator inner ring, therefore the static pressure on 103 right side of stator inner ring
For PS2.It is known that compressor stator blade 102 has diffusion action, therefore inlet pressure is less than outlet pressure, i.e. PS1< PS2,
In this way, the static pressure on the right side of stator inner ring 103 is greater than the static pressure in 103 left side of stator inner ring, gas under the driving effect of pressure difference, from
Left side is leaked on the right side of labyrinth gas seals structure, under the same conditions, pressure difference is bigger, and leakage flow is bigger.
To reduce leakage flow, the present invention proposes a kind of improved turbomachine of structure.As shown in Fig. 2, illustrating at one
Property embodiment in, turbomachine includes device for preventing leakage, multiple stator blades 1 and multiple rotor blades 2, stator blade 1 with turn
2 arranged for interval of blades forms the first cavity, stator blade between the side of stator blade 1 and rotor blade 2 adjacent thereto
The second cavity is formed between 1 other side and another rotor blade 2 adjacent thereto, the pressure of the first cavity is less than the second cavity
Pressure, device for preventing leakage is used to reduce pressure difference between the first cavity and the second cavity, to reduce from the second cavity flow direction
The flow of the leakage flow of first cavity.
In above-mentioned illustrative examples, by the way that device for preventing leakage is arranged, can reduce the first cavity and the second cavity it
Between pressure difference, weaken driving force from the second cavity to the first cavity that flow from of air-flow, reduce the flow of leakage stream, to improve
The efficiency and stability margin of turbomachine.Moreover, with the increase of revolving speed, although the pressure difference between the first cavity and the second cavity
It can increase accordingly, but the ability of device for preventing leakage reduction pressure difference can also increase with the increase of revolving speed, therefore can be adaptively
Meet the increased requirement of balance of pressure difference between the first cavity and the second cavity, vice versa when revolving speed reduces.
In above-mentioned illustrative examples, the first cavity and the second cavity can be specially with stator blade 1 below
4 two sides of stator inner ring that stator listrium 3 connects are formed by cavity.
Preferably, device for preventing leakage is arranged in the first cavity and/or the second cavity, more directly, efficiently to first
Pressure difference between cavity and the second cavity is adjusted.
Specifically, turbomachine further includes multiple wheel discs 5, and rotor blade 2 is mounted on wheel disc 5, two neighboring wheel disc 5 it
Between connected by drum barrel 6, device for preventing leakage is arranged on drum barrel 6.By being arranged device for preventing leakage on drum barrel 6, can borrow
The rotation for helping wheel disc 5 and drum barrel 6 rotates device for preventing leakage with wheel disc 5 and drum barrel 6, in rotary course, anti-leak dress
It sets the pressure that can increase the first cavity and the effect to air-flow or reduces the pressure of the second cavity.
Further, device for preventing leakage can be integrally formed with drum barrel 6, can also be welded on drum barrel 6.Wherein, prevent letting out
Leakage device can be processed with complete machine, can also be separately machined with piecemeal.
As a preferred embodiment of turbomachine of the present invention, device for preventing leakage includes supercharging device, and supercharging device is set
It sets in the first cavity, so that the pressure rise of the first cavity；And/or device for preventing leakage includes dropping equipment, dropping equipment is set
It sets in the second cavity, so that the pressure reduction of the second cavity.
By individually increasing the pressure of the first cavity, perhaps individually reduces the pressure of the second cavity or increase by the simultaneously
The pressure of one cavity and the pressure for reducing the second cavity, can reduce the pressure difference between the first cavity and the second cavity, reach
To the purpose for reducing leakage flow.
Specifically, supercharging device includes radial flow impeller machinery or mixed flow compressor tool；And/or dropping equipment packet
Include radial flow impeller machinery or mixed flow compressor tool.
Wherein, the airintake direction of radial flow impeller machinery and outgassing direction angle are 90 °, just with the root of stator blade
The flow direction of two sides leakage stream has the characteristics of steering mutually to agree with, and satisfaction flows to demand, can more effectively realize boosting or drop
The effect of pressure；Angle between the airintake direction and outgassing direction of mixed flow compressor tool also can to a certain extent less than 90 °
Enough realize the effect of boost or depressurization.
Preferably, supercharging device includes centrifugal impeller 8, and the pressure rise of the first cavity can be made by centrifugal impeller 8；
And/or dropping equipment includes centripetal turbine 7, and the pressure reduction of the second cavity can be made by centripetal turbine 7.
In addition, one end of the close drum barrel 6 of stator blade 1 is equipped with stator inner ring 4, the close anti-leak of stator inner ring 4 is filled
The side set is equipped with anti-abrasive coatings.By the way that anti-abrasive coatings are arranged, can be prevented when rotor blade 2, wheel disc 5 and drum barrel 6 rotate
Mill is touched between device for preventing leakage and stator inner ring 4, reduces the abrasion to stator inner ring 4 or device for preventing leakage, improves impeller
Mechanical service life and safety in operation.
Further, there is gap between anti-abrasive coatings and device for preventing leakage.The gap is also possible to prevent device for preventing leakage
Mill is touched between stator inner ring.
Certainly, in other embodiments, anti-abrasive coatings also can be set on centrifugal impeller 8 or centripetal turbine 7, and prevent
Grinding has gap between coating and stator inner ring 4, also may be implemented to prevent from occurring between device for preventing leakage and stator inner ring in this way
Touch the purpose of mill.
Preferably, turbomachine further includes casing, and stator blade 1 is mounted on casing, the close rotor blade 2 of casing
Side is equipped with anti-abrasive coatings.The setting of the anti-abrasive coatings is in order to avoid touching mill between rotor blade 2 and casing.
To prevent from leaking, one end of the close drum barrel 6 of stator blade 1 is equipped with stator inner ring 4, stator inner ring 4 and drum barrel 6 it
Between be equipped with labyrinth gas seals structure.The labyrinth gas seals structure includes the honeycomb 15 being arranged in stator inner ring 4 and is arranged on drum barrel 6
Obturage comb tooth 14.
Based on above-mentioned turbomachine, the present invention also proposes a kind of aero-engine, which includes above-mentioned
Turbomachine.
In aero-engine embodiment of the present invention, above-mentioned turbomachine may include turbine or compressor.That is, above-mentioned
Device for preventing leakage can be set on turbine, also can be set on compressor, to be sealed between turbine or compressor stage
Sternly, leakage stream between reduction grade.
It should be noted that outlet side pressure ratio import lateral pressure is high, therefore can be in outlet side for compressor
Centripetal turbine is set, and centrifugal impeller is set in inlet side；For turbine, inlet side pressure ratio exports lateral pressure height, because
Centripetal turbine can be arranged in inlet side in this, and centrifugal impeller is arranged in outlet side.
Positive technical effect possessed by turbomachine is equally applicable to aero-engine in above-mentioned each embodiment, here
It repeats no more.
Below with reference to Fig. 2~Fig. 4 to the course of work of one embodiment of turbomachine of the present invention and aero-engine into
Row explanation:
It is illustrated so that turbomachine is compressor as an example.
As shown in Fig. 2, in one embodiment, compressor includes stator blade 1, rotor blade 2, stator listrium 3, stator
Inner ring 4, wheel disc 5 and drum barrel 6, stator blade 1 are connect with stator listrium 3, and stator listrium 3 is connect with stator inner ring 4, stator inner ring
4 left side (import) forms the first cavity, the second cavity of right side (outlet) formation of stator inner ring 4, in the first cavity and
Centrifugal impeller 8 is installed on the drum barrel 6 in 4 left side (import) of stator inner ring, in the second cavity and on the right side of stator inner ring 4 (out
Mouthful) drum barrel 6 be equipped with centripetal turbine 7.Wherein, stator blade 1, stator listrium 3 and stator inner ring 4 are stator parts, are not
Rotation, rotor blade 2, wheel disc 5, drum barrel 6 and the centrifugal impeller 8 being welded on drum barrel 6 or centripetal turbine 7 are rotor
Part and compressor revolving speed having the same, the casing and stator inner ring of centrifugal impeller 8 or centripetal turbine 7 combine together.
The right side (outlet) of stator inner ring 4 is equipped with first coating 9, and the left side (import) of stator inner ring 4 is equipped with second coating
10, and there is the first gap 11 between first coating 9 and centripetal turbine 7, have second between second coating 10 and centrifugal impeller 8
Gap 12, to prevent from touching mill between stator inner ring 4 and centrifugal impeller 8 or centripetal turbine 7.Meanwhile on the casing of compressor
Equipped with third coating 13, between third coating 13 and the top of rotor blade 2 have gap, to prevent rotation stop blades 2 with calm the anger
Mill is touched between the casing of machine.
In the prior art, when compressor rotary work, stator blade 1 has diffusion action, and are produced from 4 two sides of stator inner ring
Raw pressure difference, promotes gap of the air-flow from the high side of pressure Jing Guo labyrinth gas seals structure to flow to the low side of pressure, thus shape
At leakage stream.In an embodiment of the present invention, increase a centrifugal impeller 8 on the drum barrel 6 in 4 left side of stator inner ring, or quiet
After increasing a centripetal turbine 7 on the drum barrel 6 on 4 right side of sub- inner ring, with the rotary work of compressor, 8 diffusion of centrifugal impeller, to
The expansion decompression of vortex cordis wheel 7, so that left pressure improves or right atrial pressure reduces, the pressure difference of 4 two sides of stator inner ring is (i.e. above-mentioned
Pressure difference between first cavity and the second cavity) it reduces or eliminates, the driving force for obturaging leakage stream at comb tooth weakens, leakage stream
Amount reduces.
Meanwhile it is adaptive for reducing the degree of 4 pressure at both sides of stator inner ring difference caused by centrifugal impeller 8 or centripetal turbine 7
It answers, as the increase of rotating speed of gas compressor is mounted on drum barrel 6 although the pressure difference of 4 two sides of stator inner ring can be increase accordingly
The pressure ratio of centrifugal impeller 8 or the expansion ratio of centripetal turbine 7 can also increase with the increase of revolving speed, therefore can adaptively meet
The 4 increased requirement of balance of two sides pressure difference of stator inner ring.
Specifically, as shown in figure 3, after centripetal turbine 7 is installed on the right side of Profile For Compressor Stator inner ring 4, by vortex cordis
After 7 expansion of wheel, pressure on the right side of labyrinth gas seals structure is from PS2It is reduced to PS3, therefore the pressure difference of labyrinth gas seals structure two sides is by (PS2-
PS1) become (PS3-PS1), and PS3< PS2, therefore pressure difference reduces, leakage flow reduces.
As shown in figure 4, being compressed after centrifugal impeller 8 is installed in the left side of Profile For Compressor Stator inner ring 4 by centrifugal impeller 8
Afterwards, the pressure on the left of labyrinth gas seals structure is from PS1It is upgraded to PS4, therefore the pressure difference of labyrinth gas seals structure two sides is by (PS2-PS1) become
(PS2-PS4), and PS4>PS1, therefore pressure difference reduces, leakage flow reduces.
Pass through the explanation to turbomachine of the present invention and multiple embodiments of aero-engine, it can be seen that impeller of the present invention
Mechanical and aero-engine embodiment at least has the advantage, that the principle using centrifugal impeller pressurization, centripetal turbine decompression,
Centrifugal impeller is set on the drum barrel on the left of stator inner ring or centripetal turbine is set on the drum barrel on the right side of stator inner ring, is improved
The pressure on the right side of pressure or reduction stator inner ring on the left of stator inner ring, achievees the purpose that pressure at both sides balance or pressure difference reduce,
The driving force for obturaging leakage stream at comb tooth weakens, to reduce leakage flow, improve the efficiency of compressor or turbine and stablize abundant
Degree；Moreover, with the increase of revolving speed, although the pressure difference of stator inner ring two sides can be increase accordingly, the pressure ratio of centrifugal impeller or to
The expansion ratio of vortex cordis wheel can also increase with the increase of revolving speed, therefore can adaptively meet the increase of stator inner ring two sides pressure difference
Requirement of balance, when revolving speed reduce when vice versa.
Finally it should be noted that: the above embodiments are merely illustrative of the technical scheme of the present invention and are not intended to be limiting thereof；To the greatest extent
The present invention is described in detail with reference to preferred embodiments for pipe, it should be understood by those ordinary skilled in the art that: still
It can modify to a specific embodiment of the invention or some technical features can be equivalently replaced；Without departing from this hair
The spirit of bright technical solution should all cover within the scope of the technical scheme claimed by the invention.
Claims (13)
1. a kind of turbomachine, which is characterized in that including device for preventing leakage, multiple stator blades (1) and multiple rotor blades
(2), the stator blade (1) and the rotor blade (2) arranged for interval, the side of the stator blade (1) and adjacent thereto
The rotor blade (2) between form the first cavity, the other side of the stator blade (1) and adjacent thereto another described
The second cavity is formed between rotor blade (2), the pressure of first cavity is less than the pressure of second cavity, described to prevent letting out
Leakage device is used to reduce the pressure difference between first cavity and second cavity, is flowed to reducing from second cavity
The flow of the leakage flow of first cavity.
2. turbomachine according to claim 1, which is characterized in that the device for preventing leakage is arranged in first cavity
And/or in second cavity.
3. turbomachine according to claim 1, which is characterized in that the turbomachine further includes multiple wheel discs (5), institute
It states rotor blade (2) to be mounted on the wheel disc (5), be connected between the two neighboring wheel disc (5) by drum barrel (6), it is described
Device for preventing leakage is arranged on the drum barrel (6).
4. turbomachine according to claim 3, which is characterized in that the device for preventing leakage and the drum barrel (6) one
Molding；Alternatively, the device for preventing leakage is welded on the drum barrel (6).
5. turbomachine according to claim 1, which is characterized in that the device for preventing leakage includes supercharging device, described
Supercharging device is arranged in first cavity, so that the pressure rise of first cavity；And/or the device for preventing leakage
Including dropping equipment, the dropping equipment is arranged in second cavity, so that the pressure reduction of second cavity.
6. turbomachine according to claim 5, which is characterized in that the supercharging device include radial flow impeller it is mechanical or
Mixed flow compressor tool；And/or the dropping equipment includes radial flow impeller machinery or mixed flow compressor tool.
7. turbomachine according to claim 6, which is characterized in that the supercharging device includes centrifugal impeller (8)；With/
Or, the dropping equipment includes centripetal turbine (7).
8. described in any item turbomachines according to claim 1~7, which is characterized in that the turbomachine further includes multiple
Wheel disc (5), the rotor blade (2) are mounted on the wheel disc (5), pass through drum barrel (6) between the two neighboring wheel disc (5)
One end close to the drum barrel (6) of connection, the stator blade (1) is equipped with stator inner ring (4), the stator inner ring (4)
Anti-abrasive coatings are equipped with close to the side of the device for preventing leakage.
9. turbomachine according to claim 8, which is characterized in that between the anti-abrasive coatings and the device for preventing leakage
With gap.
10. described in any item turbomachines according to claim 1~7, which is characterized in that the turbomachine further includes machine
Casket, the stator blade (1) are mounted on the casing, and the side close to the rotor blade (2) of the casing is equipped with anti-
Grind coating.
11. described in any item turbomachines according to claim 1~7, which is characterized in that the turbomachine further includes multiple
Wheel disc (5), the rotor blade (2) are mounted on the wheel disc (5), pass through drum barrel (6) between the two neighboring wheel disc (5)
Connection, the stator blade (1) close to the drum barrel (6) one end be equipped with stator inner ring (4), the stator inner ring (4) with
Labyrinth gas seals structure is equipped between the drum barrel (6).
12. a kind of aero-engine, which is characterized in that including turbomachine as claimed in any one of claims 1 to 11.
13. aero-engine according to claim 12, which is characterized in that the turbomachine includes turbine or calms the anger
Machine.
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| CN201710893824.XA CN109578083B (en) | 2017-09-28 | 2017-09-28 | Impeller machinery and aeroengine |
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|---|---|---|---|
| CN201710893824.XA CN109578083B (en) | 2017-09-28 | 2017-09-28 | Impeller machinery and aeroengine |
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| CN109578083B CN109578083B (en) | 2021-09-03 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112065774A (en) * | 2020-09-15 | 2020-12-11 | 中国航发沈阳发动机研究所 | Cartridge receiver structure and rotor-stator structure thereof |
| CN112228382A (en) * | 2020-12-17 | 2021-01-15 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor performance test device |
| CN112240226A (en) * | 2019-07-18 | 2021-01-19 | 中国航发商用航空发动机有限责任公司 | Rotor assembly, aircraft engine and assembly method of rotor assembly |
| CN113623072A (en) * | 2021-08-23 | 2021-11-09 | 中国科学院工程热物理研究所 | Rear-stage disc edge cooling structure for high-pressure-ratio axial-flow compressor |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4405134A (en) * | 1981-01-31 | 1983-09-20 | Rolls-Royce Limited | Non-contacting gas seal for relatively rotating parts |
| CN104196751A (en) * | 2014-01-23 | 2014-12-10 | 南京航空航天大学 | Stator sealing and gas suction control corner area separation structure used for gas compressor/fan |
| CN104963886A (en) * | 2015-07-01 | 2015-10-07 | 南京航空航天大学 | Radial gap no-leakage sealing structure and method for rotor and stator of axial flow compressor or fan |
| CN106979177A (en) * | 2016-01-18 | 2017-07-25 | 通用电气公司 | Turbo-compressor stator |
-
2017
- 2017-09-28 CN CN201710893824.XA patent/CN109578083B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4405134A (en) * | 1981-01-31 | 1983-09-20 | Rolls-Royce Limited | Non-contacting gas seal for relatively rotating parts |
| CN104196751A (en) * | 2014-01-23 | 2014-12-10 | 南京航空航天大学 | Stator sealing and gas suction control corner area separation structure used for gas compressor/fan |
| CN104963886A (en) * | 2015-07-01 | 2015-10-07 | 南京航空航天大学 | Radial gap no-leakage sealing structure and method for rotor and stator of axial flow compressor or fan |
| CN106979177A (en) * | 2016-01-18 | 2017-07-25 | 通用电气公司 | Turbo-compressor stator |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112240226A (en) * | 2019-07-18 | 2021-01-19 | 中国航发商用航空发动机有限责任公司 | Rotor assembly, aircraft engine and assembly method of rotor assembly |
| CN112065774A (en) * | 2020-09-15 | 2020-12-11 | 中国航发沈阳发动机研究所 | Cartridge receiver structure and rotor-stator structure thereof |
| CN112228382A (en) * | 2020-12-17 | 2021-01-15 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor performance test device |
| CN112228382B (en) * | 2020-12-17 | 2021-03-02 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor performance test device |
| CN113623072A (en) * | 2021-08-23 | 2021-11-09 | 中国科学院工程热物理研究所 | Rear-stage disc edge cooling structure for high-pressure-ratio axial-flow compressor |
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